[Federal Register Volume 69, Number 216 (Tuesday, November 9, 2004)]
[Rules and Regulations]
[Pages 64832-64834]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-24717]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18579; Directorate Identifier 2004-CE-19-AD;
Amendment 39-13856; AD 2004-23-01]
RIN 2120-AA64
Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-7
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain
Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes with any Lear
Romec RR53710B type or Lear Romec RR53710K fuel booster pump (Pilatus
part number 968.84.11.401; 968.84.11.403; or 968.84.11.404) installed.
This AD requires you to check the airplane logbook to determine whether
any installed fuel booster pump has been modified with spiral wrap to
protect the wire leads and has the suffix letter ``B'' added to the
serial number of the fuel booster pump identification plate. If any
installed fuel booster pump has not been modified, you are required to
inspect any installed fuel booster pump wire lead for defects; if
defects are found, replace the fuel booster pump with a modified fuel
booster pump with spiral wrap that protects the wire leads; or if no
defects are found, install spiral wrap to protect any wire leads and
add the suffix letter ``B'' to the serial number of the fuel booster
pump identification plate. The pilot is allowed to do the logbook
check. If the pilot can positively determine that the fuel booster pump
wire leads with spiral wrap are installed following the service
information and that the suffix letter ``B'' is included in the serial
number of the fuel booster pump identification plate, no further action
is required. This AD is the result of mandatory continuing
airworthiness information (MCAI) issued by the airworthiness authority
for Switzerland. We are issuing this AD to detect and correct any
defects in the leads of any fuel booster pump, which could result in
electrical arcing. This failure could lead to a fire or explosion in
the fuel tank.
DATES: This AD becomes effective on December 27, 2004.
As of December 27, 2004, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulation.
ADDRESSES: To get the service information identified in this AD,
contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans,
Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; e-
mail: aircraft.com">SupportPC12@pilaltus-aircraft.com or from Pilatus Business
Aircraft Ltd., Product Support Department, 11755 Airport Way,
Broomfield, Colorado 80021; telephone: (303) 465-9099; facsimile: (303)
465-6040. To review this service information, go to the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or
call (202) 741-6030.
To view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-18579.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? The Federal Office for Civil
Aviation (FOCA), which is the airworthiness authority for Switzerland,
recently notified FAA that an unsafe condition may exist on certain
Pilatus Model PC-7 airplanes. The FOCA reports that there have been 11
reports of damaged fuel boost pump wire leads from 9 Model PC-12
airplanes that have a similar type design. Further, the FOCA reports
that it is possible that the wire leads to the left and right fuel
pumps are damaged. This could possibly cause electrical arcs from the
leads in an air/fuel mixture.
What is the potential impact if FAA took no action? Any electrical
arcing could lead to a fire or explosion in the fuel tank.
Has FAA taken any action to this point? We issued a proposal to
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to
include an AD that would apply to certain Pilatus Model PC-7 airplanes
with any Lear Romec RR53710B type or Lear Romec RR53710K fuel booster
pump (Pilatus part number 968.84.11.401; 968.84.11.403; or
968.84.11.404) installed. This proposal was published in the Federal
Register as a notice of proposed rulemaking (NPRM) on August 20, 2004
(69 FR 516161). The NPRM proposed to require you to check the airplane
logbook to determine whether any installed fuel booster pump has been
modified with spiral wrap to protect the wire leads and has the suffix
letter ``B'' added to the serial number of the fuel booster pump
identification plate. If any installed fuel booster pump has not been
modified, you are required to inspect any installed fuel booster pump
wire lead for defects; if defects are found, replace the fuel booster
pump with a modified fuel booster pump with spiral wrap that protects
the wire leads; or if no defects are found, install spiral wrap to
protect any wire leads and add the suffix letter ``B'' to the serial
number of the fuel booster pump identification plate. The pilot is
allowed to do the logbook check. If the pilot can positively determine
that the fuel booster pump wire leads with spiral wrap are installed
following the service information and that the suffix letter ``B'' is
included in the serial number of the fuel booster pump identification
plate, no further action is required.
Comments
Was the public invited to comment? We provided the public the
opportunity to participate in developing this AD. We received no
comments on the proposal or on the determination of the cost to the
public.
Conclusion
What is FAA's final determination on this issue? We have carefully
reviewed the available data and determined that air safety and the
public interest require adopting the AD as proposed except for minor
editorial corrections. We have determined that these minor corrections:
--Are consistent with the intent that was proposed in the NPRM for
correcting the unsafe condition; and
--Do not add any additional burden upon the public than was already
proposed in the NPRM.
[[Page 64833]]
Changes to 14 CFR Part 39--Effect on the AD
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997,
July 22, 2002), which governs the FAA's AD system. This regulation now
includes material that relates to altered products, special flight
permits, and alternative methods of compliance. This material
previously was included in each individual AD. Since this material is
included in 14 CFR part 39, we will not include it in future AD
actions.
Costs of Compliance
How many airplanes does this AD impact? We estimate that this AD
affects 10 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected airplanes? We estimate the following costs to do the
inspection:
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Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
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1 workhour x $65 per hour = $65..... Not applicable......... $65 $65 x 10 = $650.
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We estimate the following costs to do any necessary replacement of
any fuel boost pump, including the installation of any wire wrap, that
will be required based on the results of the inspection. We have no way
of determining the number of airplanes that may need this installation:
------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
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5 workhours x $65 per hour = $2,800 for each fuel $2,800 x $325 =
$325. booster pump. $3,125 for each
fuel booster pump
installation.
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Regulatory Findings
Will this AD impact various entities? We have determined that this
AD will not have federalism implications under Executive Order 13132.
This AD will not have a substantial direct effect on the States, on the
relationship between the national government and the States, or on the
distribution of power and responsibilities among the various levels of
government.
Will this AD involve a significant rule or regulatory action? For
the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``Docket No. FAA-2004-18579; Directorate Identifier 2004-CE-19-AD'' in
your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. FAA amends Sec. 39.13 by adding a new AD to read as follows:
2004-23-01 Pilatus Aircraft Ltd.: Amendment 39-13856; Docket No.
FAA-2004-18579; Directorate Identifier 2004-CE-19-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on December 27, 2004.
What Other ADs Are Affected by This Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects Model PC-7 airplanes, serial numbers 101
through 618, that are:
(1) equipped with Lear Romec RR53710B type or Lear Romec
RR53710K fuel booster pump, Pilatus part number (P/N) 968.84.11.401;
968.84.11.403; or 968.84.11.404; and
(2) certificated in any category.
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Switzerland. The actions specified in this AD are intended to detect
and correct any defects in the leads of any fuel booster pump, which
could result in electrical arcing. This failure could lead to a fire
or explosion in the fuel tank.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
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Actions Compliance Procedures
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(1) Check the airplane Within 50 hours time- The owner/operator
logbook to to ensure that in-service (TIS) holding at least a
any fuel booster pump (part after December 27, private pilot
number (P/N) 968.84.11.401; 2004 (the effective certificate as
968.84.11.403; or date of this AD), authorized by
968.84.11.404) has been unless already done. section 43.7 of the
modified with spiral wrap Federal Aviation
to protect the wire leads Regulations (14 CFR
and has the suffix letter 43.7) may perform
``B'' added to the serial this check.
number of the fuel booster
pump identification plate
as required by paragraph
(e)(5) of this AD.
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[[Page 64834]]
(2) If you can positively Not Applicable...... Make logbook entry.
determine that any fuel
booster pump (P/N
968.84.11.401;
968.84.11.403; or
968.84.11.404) has been
modified following the
Accomplishment
Instructions--Aircraft
section in Pilatus PC-7
Service Bulletin No. 28-
009, dated October 6, 2003,
and has the suffix letter
``B'' added to the serial
number of the fuel booster
pump identification plate
as required by paragraph
(e)(5) of this AD, then no
further action is required.
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(3) Inspect any fuel booster Within 50 hours TIS Follow the
pump (P/N 968.84.11.401; after December 27, Accomplishment
968.84.11.403; or 2004 (the effective Instructions--Aircr
968.84.11.404) leads for date of this AD), aft section in
any defects. unless already done. Pilatus PC-7
Service Bulletin
No. 28-009, dated
October 6, 2003.
This subject is
also addressed in
the Pilatus PC-7
Airplane
Maintenance Manual.
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(4) If any defect is found Before further Follow the
during the inspection flight after the Accomplishment
required by paragraph inspection required Instructions--Aircr
(e)(3) of this AD, replace by paragraph (e)(3) aft section in
the fuel booster pump. of this AD in which Pilatus PC-7
any defect is found. Service Bulletin
No. 28-009, dated
October 6, 2003.
This subject is
also addressed in
the Pilatus PC-7
Airplane
Maintenance Manual.
-----------------------------
(5) If no defects are found Before further Follow the
during the inspection flight after the Accomplishment
required by paragraph inspection required Instructions--Aircr
(e)(3) of this AD, modify by paragraph (e)(3) aft section in
any fuel booster pump (P/N of this AD where no Pilatus PC-7
968.84.11.401; defect is found. Service Bulletin
968.84.11.403; or No. 28-009, dated
968.84.11.404) by October 6, 2003.
installing the lead This subject is
inspection by using a also addressed in
spiral wrap. After doing the Pilatus PC-7
the modification, re- Airplane
identify the fuel booster Maintenance Manual.
pump (P/N 968.84.11.401;
968.84.11.403; or
968.84.11.404) by adding
the suffix letter ``B'' to
the serial number of the
fuel booster pump
identification plate.
-----------------------------
(6) Do not install any fuel As of December 27, Follow the
booster pump (P/N 2004 (the effective Accomplishment
968.84.11.401; date of this AD). Instructions--Spare
968.84.11.403; or s section in
968.84.11.404) that has not Pilatus PC-7
been modified and Service Bulletin
identified with the suffix No. 28-009, dated
letter ``B'' to the serial October 6, 2003.
number of the fuel booster
pump identification plate.
------------------------------------------------------------------------
Note 1: The FAA recommends that you incorporate Pilatus PC-7
Maintenance Manual No. 28-20-03, dated November 30, 2003, and
Pilatus PC-7 Maintenance Manual No. 12-10-01, dated November 30,
2003, in the appropriate section of the airplane maintenance manual.
Note 2: Wiring defects are addressed in paragraph 11-97 in FAA
Advisory Circular (AC) 43.13-1B.
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to
your principal inspector. The principal inspector may add comments
and will send your request to the Manager, Standards Office, Small
Airplane Directorate, FAA. For information on any already approved
alternative methods of compliance, contact Doug Rudolph, Aerospace
Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile:
(816) 329-4090.
Is There Other Information That Relates to This Subject?
(g) Swiss AD Number HB-2004-210, issue dated June 11, 2004, also
addresses the subject of this AD.
Does This AD Incorporate Any Material by Reference?
(h) You must do the actions required by this AD following the
instructions in Pilatus PC-7 Service Bulletin No. 28-009, dated
October 6, 2003. The Director of the Federal Register approved the
incorporation by reference of this service bulletin in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this
service information, contact Pilatus Aircraft Ltd., Customer Liaison
Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 6208;
facsimile: +41 41 619 7311; e-mail: aircraft.com">SupportPC12@pilaltus-aircraft.com or from Pilatus Business Aircraft Ltd., Product Support
Department, 11755 Airport Way, Broomfield, Colorado 80021;
telephone: (303) 465-9099; facsimile: (303) 465-6040. To review
copies of this service information, go to the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call
(202) 741-6030. To view the AD docket, go to the Docket Management
Facility; U.S. Department of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on
the Internet at http://dms.dot.gov. The docket number is FAA-2004-
18579.
Issued in Kansas City, Missouri, on October 29, 2004.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-24717 Filed 11-8-04; 8:45 am]
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